scholarly journals Numerical Simulation of Supersonic Carman Curve Bodies with Aerospike

2021 ◽  
Vol 2021 ◽  
pp. 1-14
Author(s):  
HaiLong Zhao ◽  
Ke Peng ◽  
ZePing Wu ◽  
WeiHua Zhang ◽  
JiaWei Yang ◽  
...  
Keyword(s):  
Numerical Simulation ◽  
Mach Number ◽  
Supersonic Flow ◽  
Drag Reduction ◽  
Numerical Simulations ◽  
Reduction Methods ◽  
Reduction Effect ◽  
Supersonic Vehicles

Drag reduction is one of the important problems for the supersonic vehicles. As one of the drag reduction methods, aerospike has been used in some equipment because of its good drag reduction effect. In this paper, the numerical simulations of Carman curve bodies with different lengths of the aerospike and different radius of the flat cylindrical aerodisk in supersonic flow freestream are investigated. Based on the numerical simulations, the mechanism of drag reduction of the aerospike is discussed. The drag reduction effect influence of the parameters of the aerodisk radius and the aerospike length on the Carman curve body is analyzed. The aerodisk radius within a certain range is helpful for the drag reduction. The change of length of the aerospike has little effect on the drag of Carmen curve bodies. The drag reduction effect of the same aerospike becomes worse with the increase of the incoming Mach number.

scholarly journals An investigation on the drag reduction performance of bioinspired pipeline surfaces with transverse microgrooves

2020 ◽  
Vol 11 ◽  
pp. 24-40 ◽  
Author(s):  
Weili Liu ◽  
Hongjian Ni ◽  
Peng Wang ◽  
Yi Zhou
Keyword(s):  
Numerical Simulation ◽  
Drag Reduction ◽  
Pressure Loss ◽  
Fluid Transport ◽  
Reduction Rate ◽  
Orthogonal Analysis ◽  
Maximum Drag Reduction ◽  
Reduction Effect ◽  
Save Energy ◽  
Microgrooved Surface

A novel surface morphology for pipelines using transverse microgrooves was proposed in order to reduce the pressure loss of fluid transport. Numerical simulation and experimental research efforts were undertaken to evaluate the drag reduction performance of these bionic pipelines. It was found that the vortex ‘cushioning’ and ‘driving’ effects produced by the vortexes in the microgrooves were the main reason for obtaining a drag reduction effect. The shear stress of the microgrooved surface was reduced significantly owing to the decline of the velocity gradient. Altogether, bionic pipelines achieved drag reduction effects both in a pipeline and in a concentric annulus flow model. The primary and secondary order of effect on the drag reduction and optimal microgroove geometric parameters were obtained by an orthogonal analysis method. The comparative experiments were conducted in a water tunnel, and a maximum drag reduction rate of 3.21% could be achieved. The numerical simulation and experimental results were cross-checked and found to be consistent with each other, allowing to verify that the utilization of bionic theory to reduce the pressure loss of fluid transport is feasible. These results can provide theoretical guidance to save energy in pipeline transportations.

scholarly journals Comparing the results of analytical method and numerical simulation method for supersonic flow over main wing of S-125 Neva/Pechora missle

2017 ◽  
Vol 20 (K1) ◽  
pp. 84-90
Author(s):  
Ha Nam Tran ◽  
Ngoc Anh Vu ◽  
Tuan Phuong Nam Le
Keyword(s):  
Numerical Simulation ◽  
Mach Number ◽  
Supersonic Flow ◽  
Analytical Method ◽  
Fluid Dynamic ◽  
Simulation Method ◽  
Turbulent Model ◽  
Ansys Software ◽  
Simulation Process ◽  
Meshing Process

This paper compares the results of Computational Fluid Dynamic (CFD) and analytical method when applying to the case of supersonic flow over main wing of S-125 Neva/Pechora surface-to-air missle. The theory of two-dimensional, steady, inviscid supersonic flow over oblique surface, equations of relations between Mach number, pressure, temperature of flow in front and behind of shock wave, details of MATLAB algorithm and Spalart-Allmaras turbulent model will be displayed in this paper. Meshing process had been done by Meshing module and numerical simulation process had been done by Fluent module of ANSYS software. The results of two methods were presented in graphs of Mach number, pressure, temperature distributions along the chord line of wing. The reasons of differences between two results will be presented at the end of this paper.

scholarly journals Assessment of different turbulence models in simulating axisymmetric flow in suddenly expanded nozzles

2018 ◽  
Vol 7 (3.29) ◽  
pp. 243
Author(s):  
Sher Afghan Khan ◽  
Mir Owais Ali ◽  
Miah Mohammed Riyadh ◽  
Zahid Hossen ◽  
Nafis Mahdi Arefin
Keyword(s):  
Numerical Simulation ◽  
Numerical Analysis ◽  
Mach Number ◽  
Numerical Simulations ◽  
Axisymmetric Flow ◽  
Turbulence Models ◽  
Experimental Results ◽  
Nozzle Flow ◽  
Axisymmetric Nozzle ◽  
Good Agreement

A numerical simulation was carried out to compare various turbulence models simulating axisymmetric nozzle flow past suddenly expanded ducts. The simulations were done for L/D = 10. The convergent-divergent nozzle has been modeled and simulated using the turbulence models: The Standard k-ε model, The Standard k-ω model and The SST k-ω model. Numerical simulations were done for Mach numbers 1.87, 2.2, and 2.58 and the nozzles were operated for NPRs in the range from 3 to 11. From the numerical analysis it is apparent that for a given Mach number and effect of NPR will result in maximum gain or loss of pressure. Numerical results are in good agreement with the experimental results.  

0302 Direct numerical simulation of turbulent flow in periodically converging-diverging pipe with drag reduction effect

2013 ◽  
Vol 2013 (0) ◽  
pp. _0302-01_-_0302-02_
Author(s):  
Hiroya MAMORI ◽  
Kaoru IWAMOTO ◽  
Akira MURATA ◽  
Hiroaki ANDO ◽  
Hanaki YANAGISAWA
Keyword(s):  
Numerical Simulation ◽  
Direct Numerical Simulation ◽  
Turbulent Flow ◽  
Drag Reduction ◽  
Reduction Effect
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